Delta IV Launches WGS-3 Mission Overview. Delta IV Medium+ (5,4) Cape Canaveral Air Force Station, FL Space Launch Complex 37

Transcription

1 Delta IV Launches WGS-3 Mission Overview Delta IV Medium+ (5,4) Cape Canaveral Air Force Station, FL Space Launch Complex 37

2 Delta IV/WGS-3 United Launch Alliance (ULA) is proud to be a part of the WGS-3 mission with the U.S. Air Force Space Command's Space and Missile Systems Center (AFSPC/SMC). The WGS-3 mission marks the 11th Delta IV launch and the first launch of the Delta IV Medium+ (5,4) launch vehicle configuration. The WGS-3 mission is the third installment of the Wideband Global SATCOM (WGS) system. The WGS satellites are an important element of a new high-capacity satellite communications system providing enhanced communications capabilities to our troops in the field for the next decade and beyond. WGS enables more robust and flexible execution of Command and Control, Communications, Computers, Intelligence, Surveillance, and Reconnaissance (C4ISR), as well as battle management and combat support information functions. WGS-3 augments the existing service available through the UHF F/O, WGS-1, and WGS-2 satellites by providing additional information broadcast capabilities. My thanks to the entire ULA team for its dedication in bringing WGS-3 to launch, and to the AFSPC/SMC for selecting Delta for this important mission. Jim Sponnick Vice President, Delta Product Line 1

3 Delta IV Medium+ (5,4) Vehicle Configuration Overview The Delta IV M+ (5,4) consists of a single Delta IV common booster core (CBC), the Delta cryogenic second stage (DCSS), and four solid rocket motors (SRMs). The CBC and the DCSS are connected by a composite cylindrical interstage adapter (ISA). The SRMs are connected to the booster by two ball-and-socket joints and four structural thrusters. The SRMs are approximately 60 in. in diameter and 53 ft. long, and are constructed of a graphite-epoxy composite. Two of the SRMs have thrust vector control (TVC) capabilities. The SRMs burn for approximately 94 seconds and are jettisoned at roughly 100 seconds into the flight. The Delta IV booster tanks are structurally rigid, and constructed of isogrid aluminum barrels, spun-formed aluminum domes, machined aluminum tank skirts, and a composite centerbody. Delta IV booster propulsion is provided by the RS-68 engine system. The RS-68 burns cryogenic liquid hydrogen and liquid oxygen, and delivers 663,000 lb of thrust at sea level. The booster's cryogenic tanks are insulated with a combination of spray-on and bond-on insulation, and helium-purged insulation blankets. The Delta IV booster is controlled by the DCSS avionics system, which provides guidance, flight control, and vehicle sequencing functions during CBC and DCSS phases of flight. The boost phase of flight ends 6 seconds after main engine cutoff (MECO), when the separation charge in the interstage adapter is fired and 16 pneumatic actuators push the spent Delta IV CBC stage and the DCSS apart. The DCSS stage propellant tanks are structurally rigid and constructed of isogrid aluminum ring forgings, spun-formed aluminum domes, machined aluminum tank skirts and a composite Intertank Truss. The DCSS is also a cryogenic liquid hydrogen/liquid oxygenfueled vehicle. It uses a single RL10B-2 engine that produces 24,750 lb of thrust. Like the CBC, the DCSS cryogenic tanks are insulated with a combination of spray-on and bond-on insulation, and helium-purged insulation blankets. An equipment shelf attached to the aft dome of the DCSS liquid oxygen tank provides the structural mountings for vehicle electronics. The structural and electronic interfaces with the spacecraft (SC) are provided by the payload attach fitting (PAF). The WGS-3 mission uses a 5-m diameter payload fairing (PLF). The PLF is a composite bisector (two-piece shell) fairing. The vehicle s height, with the 47-ft tall PLF, is approximately 217 ft, 7 in. 2

4 Delta IV Medium+ (5,4) Vehicle Second Stage WGS-3 Spacecraft 5-m Payload Fairing First Stage Solid Rocket Motors (4) Wiring Tunnel LO 2 Tank Avionics LH 2 Tank Payload Attach Fitting Interstage RL10B-2 Engine RS-68 Engine LH 2 Tank LO 2 Tank 3

5 WGS-3 Spacecraft Configuration Overview The WGS-3 spacecraft is an approximately 13,200-lb communications satellite. WGS supports communications links in the 500 MHz range of the X-band and 1 GHz range of the Ka-band spectra. WGS can filter and route up to GHz of instantaneous bandwidth. Depending on the mix of ground terminals, data rates, and modulation schemes employed, a WGS satellite can support data transmission rates between 2.4 and 3.6 Gbps. WGS has 19 independent coverage areas that can be positioned throughout its field of view. This includes eight steerable/shapeable X-band beams formed by separate transmit/receive phased arrays; 10 Ka-band beams served by independently steerable diplexed antennas (three with selectable RF polarization); and transmit/receive X-band Earth-coverage beams. WGS can tailor coverage areas and connect X-band and Ka-band users anywhere within its field of view. Four Army Wideband Satellite Operations Centers (WSOCs) provide command and control of WGS. Each Global SATCOM Configuration and Control Element (GSCCE) has the capability to control up to three satellites at a time, using X-band or Ka-band telemetry and command links. Spacecraft platform control is accomplished by the 3rd Space Operations Squadron at Schriever Air Force Base in Colorado Springs, CO, using WGS mission-unique software and databases. Support technologies for WGS include the xenon-ion propulsion system (XIPS), which is 10 times more efficient than conventional bipropellant systems, highly efficient triple-junction gallium arsenide solar cells, and deployable radiators with flexible heat pipes. Four 25-cm XIPS thrusters remove orbit eccentricity during transfer orbit operations. The thrusters are also used to perform orbit maintenance and any required station-change maneuvers during the mission s life. The triple-junction gallium arsenide solar cells provide on-orbit electrical power for the spacecraft. The deployable radiators flexible heat pipes provide increased radiator area, resulting in a cooler, more stable thermal environment for the spacecraft. 4

6 WGS-3 Spacecraft SC Forward Omni Antenna (S-Band) Payload Fairing 47.0 ft ft WGS Spacecraft XIPS Thrusters (4) Spacecraft Launch Vehicle Adapter Payload Attach Fitting Illustration courtesy of The Boeing Company 5

7 WGS-3 Mission Overview The WGS-3 mission will be flown from Space Launch Complex 37 (SLC-37) at Cape Canaveral Air Force Station, FL on a Delta IV Medium+ (5,4) vehicle with four SRMs and the single-engine DCSS. The payload will be encapsulated in a 5-meter diameter payload fairing and integrated to the DCSS using a ULA payload attach fitting and a space vehicle contractor (SVC)-provided spacecraft launch vehicle adapter (SCLVA) with separation system and electrical harness. The WGS-3 payload consists of a single communications satellite. The two-burn, minimum-residual-shutdown mission will fly an easterly trajectory from SLC-37 with an approximately 101-degree flight azimuth. The separation event will release the WGS-3 spacecraft into a supersynchronous transfer orbit with a 237-nautical mile (nm) perigee, an apogee radius of approximately 36,167 nm, and an approximately 24-degree inclination. Launch begins with RS-68 engine ignition approximately 5.5 seconds before liftoff (T-5.5 seconds). SRM ignition takes place at T-0.02 seconds after telemetry indication of healthy RS-68 startup. Liftoff occurs at T+0.0 seconds. Shortly after the vehicle clears the pad, it performs its pitch/yaw/roll program. Maximum dynamic pressure occurs approximately 50 seconds into flight. The SRMs burn out at approximately T+94 seconds, and are jettisoned in pairs at T+100 and 102 seconds. Payload fairing jettison takes place at approximately 206 seconds. MECO occurs at approximately 246 seconds. 6

8 WGS-3 Mission Overview (concl d) DCSS separation is about 6 seconds after MECO. DCSS main engine start occurs 13 seconds after the separation event. At approximately 20 minutes into the mission, second stage engine cutoff 1 (SECO-1) occurs and DCSS has achieved its parking orbit. After an 8-minute coast phase, DCSS reorients itself for its restart. Restart ignition takes place approximately 28 minutes into the mission and lasts about 3 minutes. After SECO-2, DCSS re-orients its attitude for the separation event. The WGS-3 spacecraft separates about 41 minutes after launch. The turn to Collision and Contamination Avoidance Maneuver (CCAM) attitude begins about 3 minutes after the separation event. The DCSS mission ends 79 minutes after launch after blowdown of the propellant tanks and burn off of residual hydrazine. Telemetry data are gathered by TEL-4, Jonathan Dickinson Missile Tracking Annex (JDMTA), Antigua, Hartebeesthoek (HBK), and Diego Garcia Tracking Stations. The Tracking and Data Relay Satellite System (TDRSS) will also participate in gathering telemetry during the WGS-3 mission. 7

9 Delta IV Launch History Flight Configuration Mission Launch Date Delta 293 Medium+ (4,2) Eutelsat W5 20 Nov 2002 Delta 296 Medium DSCS III A3 10 March 2003 Delta 301 Medium DSCS III B6 29 Aug 2003 Delta 310 Heavy Heavy Demo 21 Dec 2004 Delta 315 Medium+ (4,2) GOES-N 24 May 2006 Delta 317 Medium+ (4,2) NROL Jun 2006 Delta 320 Medium DMSP F17 4 Nov 2006 Delta 329 Heavy DSP Nov 2007 Delta 337 Heavy NROL Jan 2009 Delta 342 Medium+ (4,2) GOES-O 27 Jun 2009 Delta IV Naming Convention Delta IV Medium+ (5,4) Vehicle Class Payload Fairing Diameter (in Meters) Number of Solid Rocket Motors 8

10 Delta IV Processing Overview Brigham City, UT Solid Rocket Motor Fabrication Decatur, AL Payload Fairing/Adapter Fabrication Booster Fabrication Second Stage Fabrication Cape Canaveral Air Force Station, FL Payload Processing & Encapsulation Launch Vehicle Processing Encapsulated Payload Mating Launch 9

11 Delta IV Hardware Flow at the Eastern Range Delta Mariner Delivers the CBC, 5-m Upper Stage, and 5-m Fairing to Launch Site GEM-60 Solid Rocket Motors Transportation to Launch Pad Testing of CBC and Second Stage at the Horizontal Integration Facility Transport to Launch Pad Erect Vehicle on Launch Pad Attach GEM-60s to Launch Vehicle Payload Encapsulation in Parallel to Delta IV Vehicle Processing Erect and Store Fairing Install Payload Attach Fitting on Buildup Stand Integrate Payload to PAF and Perform Integrated Checkout Payload Processing Facility Prepare Fairing Bisectors for Payload Encapsulation Encapsulate Payload Transport Payload to Launch Pad Launch Payload Lifted by Crane and Attached to Launch Vehicle 10

12 Launch Site Overview Mobile Service Tower (MST) LH 2 Storage Tank LO 2 Storage Tank Lightning Protection Towers Launch Table Horizontal Integration Facility (HIF) 11

13 WGS-3 Flight Profile Stage I-II Separation t = sec Alt. = 99.5 nm Range = nm V = 16,557.7 fps Second Stage Ignition t = sec Alt. = 109 nm Range = nm V = 16,451.7 fps Second Stage Restart 1 t = 1,697.4 sec Alt. = nm Range = 5,299.6 nm V = 28,585.8 fps SECO-2 t = 1,881.8 sec Alt. = nm Range = 6,088.3 nm V = 33,009.3 fps Orbit = 237 x 36,167 nm at 24 deg Inclination (290.3 x 19,420.1 nm) MECO t = sec Alt. = 94.9 nm Range = nm V = 16,534.6 fps Fairing Jettison t = sec Alt. = 68.3 nm Range = nm V = 11,958.2 fps Jettison Two TVC GEM-60s t = sec Alt. = 22.3 nm Range = 20.3 nm V = 5,238.8 fps SECO-1 t = 1,211.9 sec Alt. = nm Range = 3,179.3 nm V = 29,565.8 fps Orbit = 100 x nm at deg Inclination Spacecraft Separation t = 2,431.8 sec Alt. = 1,414.9 nm Range = 8,071.8 nm V = 29,098.5 fps Orbit = 238 x 36,109 nm at 24 deg Inclination (291.0 x 19,323* nm) Jettison Two GEM-60s t =100.0 sec Alt. = 21.4 nm Range = 19 nm V = 5,144.2 fps Liftoff (Ignite Four GEM-60s) 12

14 WGS-3 Ground Trace Longitude (deg) TEL4 = Eastern Range Station at KSC/CCAFS ANT= Eastern Range Station at Antigua TDRS = NASA Tracking and Data Relay Satellite HBK = South African Hartebeesthoek Station DGS = AFSCN Diego Garcia (REEF) Station GTS = AFSCN Guam (GUAM) Station TEL4 ANT TDRS HBK 5 DGS GTS Geodetic Latitude (deg) = MECO (246.3 sec) 2 = SECO (1,211.9 sec) 3 = SII Burn 2 Ignition (1,697.4 sec) 4 = SECO-2 (1,881.8 sec) 5 = S/C Separation (2,431.8 sec) 6 = CCAM (2, ,839.8 sec) 7 = End H2 Depletion (3,281.3 sec) 8 = End O2 Depletion (3,399.6 sec) 9 = End N2H4 Depletion (4,713.3 sec)

15 Sequence of Events Liftoff to Spacecraft Separation Event Stage I Liftoff Mach Number = 1.05 Maximum Dynamic Pressure (2) GEM60 Burnout (Fixed Nozzle) (2) GEM60 Burnout (TVC Nozzle) Jettison (2) GEM60 Casings (Fixed Nozzle) Jettison (2) GEM60 Casings (TVC Nozzle) Jettison Fairing Initiate Booster Throttle-Down Main Engine Cutoff (MECO) Stage I-II Separation Stage II Ignition Signal First Cutoff - Stage II (SECO-1) First Restart - Stage II Second Cutoff - Stage II (SECO-2) Spacecraft Separation Time After Liftoff (Sec) , , , ,

16 Delta IV Countdown (T-0 Day) Wed Nov 18 10:00 AM 11:00 AM 12:00 PM 1:00 PM 2:00 PM 3:00 PM 4:00 PM 5:00 PM 6:00 PM 7:00 PM 8:00 PM 9:00 PM 10:00 PM 11:00 PM L-8:00 L-7:00 L-6:00 L-5:00 L-4:00 L-3:00 L-2:00 L-1:00 T-05:15 T-05:15 T-04:00 T-03:00 T-02:00 T-01:00 T-00:05 T-00:05 Final Pad clear (Task 1) Test Initiation Avionics & Data Interrupt Test Hold Fire Checks MLO Test Propulsion Pre-Loading Valve Functionals 60 minute Built-in Hold Weather briefing C-Band Beacon, Range Interrogation Call to stations / Pre-task Briefing Pad Clear (Required) Post-Pad Clear Propellant Loading Preps (Hydraulic Turn-On, Low Flow Purges, ECU Bit Test) SS Pre-Loading Purge Cycles CBC & US GHe Bottle - Final Press CBC LOX Chill CBC LOX Fill CBC LOX APC, Vent/Relief, and POGO Tests LH2 Storage Tank Pressurization CBC LH2 Tank Cold Gas Chilldown CBC LH2 Slowfill CBC LH2 Fastfill CBC LH2 Tank APC/VR Test SS LOX Chill SS LOX Fill SS LOX APC Test SS LH2 Chill SS LH2 Fill SS LH2 APC Test RF Link Checks CRD Open Loop Testing Flight Slews Load Relief Wind Data Loading 15 minute built-in Hold T-5 & Counting T-0 (19:45 L / 00:45 UTC) Launch Window (0H 45M) 15

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